Abstract
In recent decades, solid fuel combustion propulsion of spacecraft has become one of the most popular choices for rocket propulsion systems. The reasons for this success are a wide range of applications, lower production costs, simplicity, and safety. The rocket’s plumes leave the nozzle at high temperatures; hence, the knowledge of produced infrared (IR) emissions is a crucial aspect during the design and tests of the rocket motors. Furthermore, rocket plume composition is given by N2, H2, H2O, CO and CO2, while solid rocket motors (SRM) additionally inject some solid particles, given by metal fuel additives in the propellant grain, i.e., aluminum oxide (Al2O3) particles. The main issue is the detection of the particles remaining in the atmosphere due to the exhaust gas of the solid rocket propulsion system that could have effects on ozone depletion. The experimental characterization of SRM plumes in the presence of alumina particles can be conducted using different optical techniques. The present study aims to review the most promising ones with a description of the optics system and their potential applications for SRM plume measurements. The most common measurement techniques are infrared spectroscopy imaging, IR imaging. UV–VIS measurements, shadowgraph, and Schlieren optical methods. The choice of these techniques among many others is due to the ability to study the plume without influencing the physical conditions existing in and around the study object. This paper presents technical results concerning the study of rocket engines plumes with the above-mentioned methods and reveals the feasibility of the measurement techniques applied.
Highlights
In rocket motors, hot gases are produced in the combustion chamber and expelled through the nozzle and interact with the air
The use and the choice of each experimental method depend on the geometrical scale, ranges of flow temperature, pressure and velocity, chemical species, and testing environment
The emissivity-based techniques have been applied to a large range of applications at both the laboratory and real solid rocket motor (SRM) scale
Summary
Hot gases are produced in the combustion chamber and expelled through the nozzle and interact with the air. There occurs the afterburning reaction due to some oxygen particles that are entrained into the plume; there is a significant rise in temperature as well as in radiation intensity for the exhaust gases. Rocket engine plumes present high temperatures, high speeds, and intense radiation. The SRM exhaust plume contains several compounds, i.e., CO, N2 , H2 , H2 O, and CO2 , and additional solid particles. In the solid propellant composition, there are additives, i.e., boron and aluminum, which increase rocket thrust. The aluminum reacts with combustion products and produces alumina (Al2 O3 ) that is collected on the burning particles surface and represents one of the main sources of high thermal infrared emission in the rocket plume; the proportion of the Al2 O3 depends on the type of propellant used [1].
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